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A characteristic inlet boundary condition for compressible, turbulent, multispecies turbomachinery flows

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Figure

Fig. 1. Rotation from cartesian basis to the normal patch basis. with δ ij the Kronecker delta and μ the dynamic viscosity
Fig. 3. Velocity vector  →  U  , and corresponding  θ and  φ angles defining the flow di-
Fig. 4. 2D test case.
Fig. 10.  Temporal evolucion of the ingoing acouscic w;we. for the Pt-Tc-NSCBC-NR formulation and for ax = 0 (rop)
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